Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle

被引：17

作者：

Yao, Songbai ^{[1
,2
]}

Tang, Xinmeng ^{[1
,2
]}

Wang, Jianping ^{[1
,2
]}

机构：

[1] Peking Univ, CAPT, Ctr Combust & Prop, Coll Engn, Beijing, Peoples R China

[2] Peking Univ, Coll Engn, SKLTCS, Dept Mech & Engn Sci, Beijing, Peoples R China

来源：

INTERNATIONAL JOURNAL OF TURBO & JET-ENGINES | 2017年 / 34卷 / 01期

基金：

中国国家自然科学基金;

关键词：

rotating detonation; hollow combustor; Laval nozzle; simulations; HYDROGEN-OXYGEN MIXTURE; MECHANISM; WAVE;

D O I：

10.1515/tjj-2015-0052

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The aim of the present paper is to investigate the propulsive performance of the hollow rotating detonation engine (RDE) with a Laval nozzle. Three-dimensional simulations are carried out with a one-step Arrhenius chemistry model. The Laval nozzle is found to improve the propulsive performance of hollow RDE in all respects. The thrust and fuel-based specific impulse are increased up to 12.60 kN and 7484.40 s, respectively, from 6.46 kN and 6720.48 s. Meanwhile, the total mass flow rate increases from 3.63 kg/s to 6.68 kg/s. Overall, the Laval nozzle significantly improves the propulsive performance of the hollow RDE and makes it a promising model among detonation engines.

引用

页码：49 / 54

页数：6

共 22 条

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